EP3198140A1

EP3198140A1 - Aviation beacon device for a wind turbine

Info

Publication number: EP3198140A1
Application number: EP15771052.6A
Authority: EP
Inventors: Olaf Schultz
Original assignee: Wobben Properties GmbH
Current assignee: Wobben Properties GmbH
Priority date: 2014-09-23
Filing date: 2015-09-16
Publication date: 2017-08-02
Anticipated expiration: 2035-09-16
Also published as: CN106715898B; CA2959810A1; CA2959810C; UY36318A; EP3198140B1; TWI636184B; JP2017531302A; JP6445705B2; US10132298B2; US20170284377A1; BR112017005826A2; TW201629339A; WO2016046045A1; CN106715898A

Abstract

The invention relates to an aviation beacon device for a wind turbine. Said aviation beacon device, which is to be arranged on a nacelle of the wind turbine, comprises at least three omnidirectional portions that are annularly and concentrically arranged about a common central axis; each omnidirectional portion comprises a lens portion which is annularly and concentrically arranged about the central axis and which has a radiation plane extending perpendicularly to the central axis and at least one illuminant ring having illuminants, annularly and concentrically arranged about the central axis, for emitting light through the lens portion; each illuminant ring is prepared to emit light in a central emitting direction (370, 371, 372) that extends at a certain emission angle (380, 381, 382) relative to the radiation plane, the emitting direction being dependent on an axial position of the illuminant ring in relation to the lens portion; at least one omnidirectional portion includes at least two axially offset illuminant rings for emitting light at different emission angles.

Description

Flight lighting device of a wind turbine

The present invention relates to a flight firing device of a wind turbine for placing on a nacelle and / or on the tower of the wind turbine. Furthermore, the present invention relates to a wind energy installation having such a flight lighting device and a method for operating such a flight control device.

Wind turbines that generate electricity from wind and feed it into an electrical supply network are well known. An example of such a wind turbine is shown schematically in FIG.

Usually, modern wind turbines have a flight firing device, ie a device for firing a wind turbine. Such facilities are mandatory for most wind turbines, due to the structural height, and have the task aviation, especially the pilots, by emitting light or radio signals to warn of aviation obstacles, such as a wind turbine. Depending on the location and the prevailing standards and laws, the most diverse requirements are placed on a flight lighting device, in particular on the vertical beam angle, the flashing clock and the intensity and wavelength of the signal.

It would be desirable that the emitted signal only reaches that for which the signal is intended and if possible does not disturb the environment. From US Pat. No. 3,858,041, for example, a mechanical device is known with which a radiation downwards to the ground is prevented or reduced. This prevents, inter alia, that people are disturbed by the signal of the flight lighting device, in particular dazzled. The disadvantage of this solution is mainly the fact of the mechanical design. The German Patent and Trademark Office has in the priority application for the present application the following state of the art research: DE 10 2010 027 527 A1 and DE 20 2007 005 003 U1.

The object of the present invention is therefore to address at least one of the aforementioned problems. In particular, the known state of the art is to be improved and a flight beacon device is proposed which dispenses with an additional mechanical device for controlling the emission of a signal. At least an alternative solution should be proposed compared to the previously known. According to the invention, a flight firing device according to claim 1 is proposed.

It is thus proposed a flight firing device of a wind turbine for arranging on a nacelle of the wind turbine, comprising at least three circular and concentrically arranged around a common center axis round beam sections. Each round beam section has a ring-shaped and concentrically arranged around the central axis lens section, with a plane defined perpendicular to the central axis beam plane, and at least one bulb ring with annular and concentric about the central axis arranged bulbs for emitting light through the lens portion. In this case, each luminous means ring is prepared for emitting light with a central, vertical emission direction, which has a radiation angle with respect to the plane of the beam, and wherein the emission direction depends on an axial position of the luminous element ring relative to the lens segment. Wherein at least one of the omnidirectional sections has at least two illuminant rings offset axially relative to one another for emitting with different emission angles. Due to the annular structure of the flight firing device through the circular beam sections, the flight firing device is set up to emit the light in a 360 ° horizontal direction. All omnidirectional sections are arranged around the same concentric axis and as intended one above the other. With the same outer diameter, they thus form an approximately cylindrical structure. However, they can in principle also have different diameters.

An omnidirectional section is thus an annular arrangement with a lens section and one or more illuminant rings. The lens section is in particular completely encircling and may, for example, be formed as a belt lens, in particular of a light-permeable and weather-resistant material, such as plastic or glass. The lens sections of all the round beam sections together can simultaneously form a housing or housing section of the flight control device. A lens section may also be composed of two or more nested lens subsections. Such lens subsections may be, for example, lens rings of different diameters intermeshed. The concrete structure also depends on the chosen bulbs. The bulbs, such as light emitting diodes, radiate radially outward through the lens portion. The bulbs do not emit a single beam, but give off the light in one area. After the light has passed through the lens or the lens section, it has a mean beam direction. This is characterized by a radiation angle, which is defined in relation to the beam plane. According to the invention, if the flight-lighting device is set up in such a way that the central axis runs vertically, the steel plane is a horizontal plane. The radiation angle is a related vertical angle.

If the mean radiation direction is then horizontal, the beam angle is 0 °. If the medium radiation direction is directed upward, the radiation angle is positive, otherwise negative.

The emission direction is determined in particular by the way in which the illuminants are aligned with respect to the lens, which in this case is simplifying for the respectively effective part of the lens section. To put it simply, a luminous means or a luminous means ring, which lies in the plane of the beam, leads to an approximately horizontal emission, that is to say to an emission angle of 0 °. If the illuminant or the luminous means ring lies below the beam plane, this results in a radiation upward, otherwise downwards. This can also be influenced by a mean beam direction of the respective luminous means.

As a result, the average radiation direction is determined by the appropriate arrangement of the light source behind its lens to the outside. This vertical direction basically always affects the entire bulb ring. The emission direction can now be selected by a corresponding control of the lighting means. In this case, even if a plurality of illuminant rings of an omnidirectional section are activated be superimposed, the radiation directions. As a result, the emission characteristic can be influenced.

Each round beam section can be designed differently. By appropriate combination of the round beam sections and their bulbs rings many different radiation characteristics can be generated.

In this case, the lens section, in particular the two opposite transparent refractive surfaces of the lens section, is set up such that the radiation characteristic of the lens section depends both on the axial position of the illuminant ring and the lens section and on the optical section of the lens section itself.

By means of at least one round-jet section of the at least two, preferably three or four, illuminant rings which are offset axially relative to one another along the central axis, the flight-firing device is set up to emit the light to be emitted at a different emission angle in comparison to omnidirectional sections with only one luminous means ring. In particular, the omnidirectional sections of the flight-lighting device are arranged in the axial direction with respect to one another. By arranging the round jet sections to each other in the axial direction, they are arranged one above the other when used as intended.

Preferably, the bulbs of the flight beacon are LEDs. By using LEDs, that is light-emitting diodes, as lighting means, the flight-firing device can make do with a comparatively small size. In addition, LEDs have a longer life and lower power consumption compared to conventional bulbs. In particular, in a design of the flight-lighting device as flashing light, the virtually inertia-free modulability and switchability of an LED is advantageous.

The flight firing device is preferably set up such that at least one or some of the lighting means are prepared for emitting light with a first color, in particular red, and at least one further or some further for emitting light with a second color, in particular white such that in each case a light-emitting ring is provided for emitting a color. By using at least two light sources of different colors, the flight-lighting device is set up for at least one first and at least one second operating mode. Preferably, the color red is set up for the first operating mode and the color white for the second operating mode, so that the flight firing device complies with the legal regulations of a red light for a night fire as well as the legal regulations of a white emission for a daily fire. In particular, the lighting means are arranged so that whole light-emitting means rings of a first color, in particular red, and a second colors, in particular white, are arranged to make selective activation of the individual colors advantageous. It may also be considered to send with a third color, for example green, status signals of the flight-lighting device

A particularly preferred embodiment is characterized in that at least some of the lighting means are configured as red LEDs and have a minimum intensity with a value of the following list: 10cd, 20cd, 25cd, 30cd, 32cd, 32.5cd, 50cd, 70cd, 100cd, 200 cd or 2000 cd.

By using red LEDs having a minimum intensity with one of the above values, it is possible in particular by a clever combination of LEDs to meet the legislator's requirements for a night fire by the use of, in particular inexpensive, red standard LEDs. A further particularly preferred embodiment is characterized in that at least some of the lighting means are designed as white LEDs and have a minimum intensity with a value of the following list: 3.4 cd 34 cd or 175 cd, the photometric values or peak values describing and the effective Intensity 2 cd, 20 cd or 100 cd. By using white LEDs that have a minimum intensity of 20,000 cd, 50,000 cd, 100,000 cd or 200,000 cd, it is possible, in particular, through a clever combination of LEDs, to meet the legislator's requirements for a daily fire by using, in particular inexpensive, white standard LEDs implement. The flight firing device preferably has a control unit, which is set up to vary the emission characteristic of the flight firing device by selective activation of individual light sources, light source groups or light source rings. The control unit is set up in such a way that it activates each individual light source, or groups of bulbs or bulbs, in particular on and off, and thereby sets a radiation characteristic of the flight beacon. The control unit is set up to control up to 600 light sources or more selectively. Under illuminant groups, for example, adjacent bulbs and / or sections of bulbs are summarized. By virtue of the fact that the lighting means and / or lighting means groups and / or lighting means rings are selectively activated, the flight lighting device is set up for a multiplicity of different radiation characteristics. The emission characteristic which can be influenced thereby comprises, in particular, the parameters: emission intensity, color, emission angle, both horizontally and vertically, and thereby also a radiation range. This can be achieved by appropriately activating the lighting means, lighting groups and / or lighting rings.

Furthermore, the control unit of the flight firing device is characterized in that the control unit has fixed programmed emission characteristics.

Fixed-programmed radiation characteristics can be provided to fulfill the general requirements of the legislator prevailing at the location of the wind turbine by programming. It can thereby be used for different regions or countries the same flight lighting facilities, but with different programming. As a result, not many individually different flight lighting devices need to be manufactured, but it may possibly be sufficient for many countries. These fixed programmed radiation characteristics are reprogrammed prior to the placement of the flight beacon on the nacelle or reprogrammed after changing the laws and / or prevailing requirements at the site.

Preferably, by the control unit of the flight lighting device during operation of the system, in particular event-dependent, to be changed.

Due to the event-dependent setting of emission characteristics, it is possible to flexibly adapt the flight-firing device to situations and to optimize them. For example. It is proposed to adapt the flight lights to this aircraft according to vertical and horizontal radiation characteristics only when an approaching aircraft. The flight lighting device then needs to emit, for example, only in the direction of the aircraft. This can also reduce the impact on the environment be because it is emitted as little light and therefore less disturbing.

On the other hand, an approaching flock of birds could be intentionally blinded and moved to twist off, or part of the flight lights could be designed and controlled to serve as a guide for migratory birds.

According to one embodiment, a flight firing device is proposed, which is characterized in that at least one emission characteristic is firmly implemented. It has been found that in many cases, a changeover is not required and instead can be fixed by suitable choice of the radiation characteristic.

It is favorable to provide an adaptation to different local requirements. Such requirements are often legal requirements and can be firmly implemented when the wind turbine is installed and the flight lights are installed. It can thus be provided for many different locations, ideally for each place in the world, a universal flight lighting device for which then only at the respective location their characteristics must be implemented.

This particularly applies to the red radiation characteristic, ie the night fire, for which very different regulations can exist.

Implementation of the at least one fixed characteristic may be accomplished by hardware measures such as disconnecting unneeded supply or control lines, or appropriate switches may be provided. However, it is also possible to provide the fixed implementation by means of a controller.

Preferably, at least one fixedly implemented emission characteristic is provided, which radiates essentially only upwards, in particular in such a way that the flight lighting device does not radiate downwards when used as intended on the wind energy plant. This is based on the knowledge that an emission characteristic only upwards, ie from a horizontal plane upwards, is sufficient for the safety of air traffic. Disruptions of the population and / or road traffic can be safely and permanently excluded. We also avoid programming errors. Instead of a changeable characteristic, which creates the possibility to switch off downwards emitting light, if it disturbs and does not need is proposed, it is now proposed to provide in the lower area basically no radiation. An adaptation to different situations is avoided, whereby a faulty switching is avoided, and for the safety of the aircraft, it is still sufficient. Such a radiation characteristic only upwards is achieved in an advantageous manner by a structure according to at least one embodiment described above. In particular, the arrangement of the bulb rings relative to the corresponding lens portion provides a simple way this possibility to realize such a radiation characteristic. It needs no special design of the lens to be provided and no cover or the like.

Another embodiment proposes a flight firing device which is characterized in that at least one fixedly implemented emission characteristic has a lower emission angle of at least -5 °, in particular approximately -2 °, below which lower emission angle the intensity is less than 10%, in particular less than 5% of the maximum intensity of the radiation characteristic is. This is preferably provided for a radiation characteristic which radiates substantially upwards, which is only very weak in the region below -5 ° or -2 °. It should be noted that even a significantly lower value than the maximum light intensity occurring in the emission characteristic is perceived as significant and thus even a reduction of the light intensity at an emission angle of 0 ° to 60% can be regarded as a radiation upward.

Preferably, it is thus proposed that the light intensity at an emission angle of 0 ° is less than 70%, preferably less than 60%, in particular less than 50%, of the maximum intensity of the emission characteristic and, in particular, decreases further with smaller emission angles. For the sake of illustration, reference is also made to FIG. 7 which will be described later.

Preferably, the flight firing device emits only upwards, with a sharp separation is hardly or only consuming possible. However, it was recognized that to avoid disturbing light on the ground is sufficient if only small amounts of light, so only a small luminous flux reaches the ground. A small part can thus be admitted. According to one embodiment it is provided that at least two permanently implemented radiation characteristics are provided, of which one is provided for a red night fire and a second for a white day fire. These two fixedly implemented radiation characteristics can also be the same, but they differ in intensity and, of course, in color.

A flight firing device is also proposed with a rod-shaped main body for horizontal passage through a tower of the wind turbine from the inside to the outside, in particular through a corresponding hole in the tower, namely in its tower wall, or for arranging on the outside of the tower, and a luminous section for radiating A light for warning aircraft, wherein the lighting section is prepared to illuminate only an area above a horizontal plane in which the flight lighting device is arranged.

It has been recognized that a large part of the disruptive effects of wind turbines on wind turbines emanates from firing of the tower and often not or not only from the flight lights on the gondola. It is therefore proposed to arrange these Flugbefeuerungen the tower so that they radiate only horizontally and upwards, thereby avoiding disturbing effects especially for the population and the road. This can be achieved by rod-shaped lights that are pushed from the inside through the tower to the outside, or they are mounted directly outside.

According to one embodiment, the flight-lighting device is characterized in that infrared illuminants are provided for emitting infrared light, in particular that at least one luminous means ring has infrared illuminants, in particular infrared LEDs. Such a flight lighting device can also or particularly well warn airplanes that work with night vision devices and can especially hard to detect red beacons at night.

Such infrared illuminants can be provided in particular as at least one luminous means ring, or can supplement a luminous means ring, ie be arranged between other illuminants. Especially between other LEDs, especially red LEDs, it can be provided for infrared LEDs. The red and infrared bulbs can then be operated simultaneously and aircraft or pilots with or without night vision device can simultaneously become aware of the obstacle. This grain The combination of red and infrared illuminants is basically proposed for each embodiment.

Preferably, a wind energy installation is provided at least with a flight lighting device according to one of the preceding embodiments.

By setting up a wind energy layer with at least one flight-lighting device, the wind energy plant is largely recognizable as an obstacle to flight during the day and at night. Preferably, a wind turbine is set up for permanent illumination in a 360 ° horizontal direction with at least two flight-lighting devices. For example, the second flight-lighting device illuminates the sectors in which no illumination by the first flight-lighting device takes place, for example due to defective bulbs and / or coverage by a rotor blade illuminated by the first flight-beaconing device.

In particular, since a rotor blade in each case can temporarily and temporarily conceal a flight firing device during its movement, a second flight firing device is frequently provided. Where, however, a cover by a rotor blade can not occur, that is, in simple terms, to the rear, the two flight lighting devices do not need to radiate twice. You can there, for example, each one 90 ° sector does not emit. This can be achieved by a pre-programmed, fixed setting.

Preferably, a method for operating a flight firing device according to one of the above explained embodiments is proposed, wherein the lighting means are controlled so that a predetermined emission characteristic is generated and / or switched on and / or off in a predetermined sector.

According to a further embodiment, it is proposed that only a few illuminants, e.g. only every second to control, thereby reducing the emission intensity.

In particular, the method proposes to control radiation characteristics of the illustrated flight-beaconing devices, especially when operated on a wind turbine. The lighting means can be controlled so that a predetermined, for example, hard-programmed, radiation characteristic is generated, wherein the predetermined radiation characteristic is retrieved, for example, from an electronic memory. Individual predetermined sectors of the emission characteristic can also be switched on and / or off, for example at a specific time.

According to one embodiment, the property of the emission of the flight-lighting device can be adjusted or changed during operation by appropriate actuation of the lighting means and / or light-emitting means rings.

In order to enable effective control of the flight firing device for many location and / or events, an activation of the lighting means, groups of bulbs and / or bulbs rings is done so that the emission of the flight beacon device is thereby changed during operation, for example in an approaching aircraft. This can be achieved for example by switching on and / or off. Furthermore, it is proposed to set or change a vertical radiation characteristic, a horizontal sector for emitting and / or a radiation intensity during operation, in particular as a function of an event and / or a period or time.

By detecting an event, for example by a sensor connected to a flight lighting device, the emission characteristic of the flight lighting device is changed over a period of time, for example for the duration of an overflight of an aircraft, or from a point in time, for example at a specific daytime or nighttime set. In this case, according to one embodiment, it is possible to switch between a permanently implemented first emission characteristic of a red night-fire and a permanently implemented second emission characteristic of a white day-fire.

Preferably, an emission characteristic is predetermined by a determination of the activation of the lighting means, in particular light-emitting rings, before the flight-lighting device is put into operation. According to one embodiment, an implementation of a fixed emission characteristic or a plurality of fixed emission characteristics takes place before the flight-firing device is put into operation. The device can be made universally, but at the site to the local conditions and / or local regulations are adjusted and it is a false control avoided. In particular, such Fehlansteuerungen are avoided, which are desirable in other places, but at the specific location are undesirable or even inadmissible.

According to one embodiment, it is also proposed to adjust or to vary the emission characteristic in the horizontal direction, in particular sectorwise. For example. In the vicinity of an airfield, the emission characteristic, in particular also the emission angle, can be provided differently in one direction to the airfield than in a direction facing away from the airfield, because airplanes departing from one direction and landing from the other direction. However, if the flight-lighting device is installed on a nacelle of a wind turbine, the horizontal orientation of the flight-firing device changes with the azimuth adjustment of the wind turbine. It is thus proposed to control the flight-firing device as a function of the azimuth position of the nacelle, in particular to adapt a radiation characteristic which varies in the horizontal direction in accordance with the azimuth position. The present invention will now be explained in more detail by way of example with reference to exemplary embodiments with reference to the accompanying figures.

Fig. 1 shows a schematic representation of a wind turbine.

2 shows a schematic representation of a flight-lighting device according to an embodiment. 3 shows a schematic representation of emission characteristics

A flight firing device according to an embodiment.

Fig. 4 shows schematically a wind turbine gondola in a plan view.

5 shows, by way of example, a vertical emission characteristic of an omnidirectional section. 6 shows by way of example a further vertical emission characteristic of an omnidirectional section.

Fig. 7 shows schematically a radiation characteristic only for a radiation upward in a comparison. 1 shows a wind energy plant 100 with a tower 102 and a nacelle 104. A rotor 106 with three rotor blades 108 and a spinner 110 is arranged on the nacelle 104. The rotor 106 is set in rotation by the wind in rotation and thereby drives a generator in the nacelle 104 at. On the nacelle 104, a flight firing device 101 is arranged, alternatively, for example, two flight firing devices 101 may be provided.

FIG. 2 shows a flight firing device 200 which has three circular-jet sections 210, 211 and 212, which are arranged annularly and concentrically with each other in the axial direction 202 around a central axis 204. The omnidirectional sections 210, 21, and 212 each include a complete circumferential lens section 220, 221, and 222, each of the lens sections 210, 21 1, and 212 defining a beam plane 230, 231, and 232. The omnidirectional sections 210 and 211 each have three completely encircling bulb rings 240, 241 and 242 or 243, 244 and 245. They have ring-shaped white LEDs 250 disposed concentrically about the central axis 204. The respective three illuminant rings 240, 241 and 242 or 243, 244 and 245 are offset axially relative to one another. The lowermost round-jet section 212 has only one light-emitting ring 246 with red LEDs 251.

2 shows a part of the flight firing device 200 in a partially sectioned, schematic partial view. The illustration of Fig. 2 - the same applies to the following Fig. 3 - is particularly possible in the vertical direction radiation characteristics are each a center bulb ring 241 and 244 at the height of the respective beam plane 230 and 231st A Leuchtmittelring 240 bzw. 243 is arranged higher in each case, and an even further luminous means ring 242 or 245 is arranged lower in each case. The two round beam sections 210 and 211 are shown identically in FIG. 2, but different configurations may also be provided. For example, the lens sections 220 and 221 may be formed differently. There may be provided a different number of bulbs rings, for example, in the upper round section 210 only two bulbs. On the one hand, the illuminant rings 240, 241 and 242 of the omnidirectional section 210 may also have different distances from one another in comparison to the spacings of the illuminant rings 243, 244 and 245 of the omnidirectional section 211. In this way, different emission characteristics can be achieved by the two omnidirectional sections 210 and 211. This can be characterized by the superposition of the radiation characteristics of the two round beam sections 210 and 21 1 very many different radiation characteristics. It is also pointed out that the vertical spacing, that is to say the spacing in the direction of the center axis 204 or in the axial direction 202 for a faraway observer, that is to say for example the pilot of an aircraft, no longer plays any role. Rather, it is much more important that different characteristics can be generated.

The omnidirectional sections 210 and 211 may also be provided to meet very different requirements for radiation characteristics. It is even conceivable that two different regions, or even two different countries, impose such different requirements on the radiation characteristics that only one circular region, such as the omnidirectional section 210, can be used for one region or one country, and for the other Region or the other country, only the operation of the omnidirectional section 21 1. Often, however, a combination of several round beam sections come into consideration.

The omnidirectional section 212 of the example of FIG. 2 has only one illuminant ring 246, which has red LEDs 251. These red LEDs or the red light ring are intended for night operation and therefore often come with less flexibility in their direction of radiation. In particular, such red light emitting diodes or even red light bulbs of flight lighting devices are less dazzling and can be easily seen even without special beam direction due to the dark environment. A single bulb ring may therefore be sufficient. Again, this is shown by way of illustration only, particularly to illustrate that a plurality of omnidirectional sections 210, 21 1, and 212 may be present in a flight firing device, which may be configured differently.

Correspondingly, it also follows from the representation of FIG. 2 that different emission characteristics can be achieved by superposing, which in addition to emission direction and intensity also includes an overlay or combination or variation with respect to the luminous color.

FIG. 3 shows the emission characteristic 300 of an omnidirectional section shown in FIG. 2. The round beam section 310 comprises a lens section 320 and three bulb rings 340, 341 and 342 represented by a respective LED 350, 351 and 352. The individual LEDs 350, 351 and 352 are selectively and as required driven by the control unit of the flight beacon 360. Characterized in that the bulb rings 340, 341 and 342 are arranged axially offset from each other, The three bulb rings 340, 341 and 342 each have a different emission characteristic. This is illustrated by radiation characteristic 301, it shows the round beam section 310 for a selective control, with only LED ring 342 or LED 352 is driven. For example, the omnidirectional section 310 shown by way of example could be identical to the omnidirectional section 210 of FIG. 2 and correspondingly form part of a flight beacon 200 as illustrated in FIG.

FIG. 3 shows this omnidirectional section 310 in two control variants. The upper variant, variant a) or Fig. 3a shows the control of all three LEDs 350, 351 and 352, which are so far representatively also for the corresponding bulb rings 340, 341 and 342. Illustratively, three beam cones 360, 361 and 362 are shown, each emanating from a light emitting diode 350, 351 and 352, respectively. These three beam cones 360, 361 and 362 then reach the lens section 320. The position of the light-emitting diodes 350, 351 or 352 relative to the lens section 320 then results in a respective emission area with a central emission direction 370, 371 or 372 with corresponding emission angles 380, 381 and 382, respectively. In this case, the light-emitting diode 350 is assigned the mean emission direction 370 with the emission angle 380. Thus, for this upper light-emitting diode 350 results in a middle emission direction 370, which is directed downward and therefore has a negative radiation angle 380. The middle LED 351 thus has a horizontal central radiation direction 371 and thus a radiation angle 381, which has the value zero. The light-emitting diode 352 arranged further down accordingly has an upwardly directed central emission direction with a positive emission angle 382.

This results in this case a) or Fig. 3a thus a broadly scattered Abstrahlcharakte- ristics, which also radiates far up and far down.

The variant b) or Fig. 3b controls only the lower LED 352, or the corresponding bulb ring, so that only the lower Abstrahlkegel 362 results and as a result, only the upward middle emission direction 372 with the beam angle 382. Thus the emission of the omnidirectional section 310 directed upwards.

When viewed from the outside or from a remote observer or observation point, the omnidirectional section 310 radiates, and if only this omnidirectional section the flight beacon device is controlled, the entire flight beacon device, in a wide range. In the lower case, the omnidirectional section 310 or the entire flight-lighting device radiates only upwards.

Thus, therefore, the characteristic of the flight lighting device can be influenced overall by appropriately targeted control of the lighting means, in particular in a bundled manner on the control of the light-emitting rings. This influence on the control makes it possible to specify both fixed characteristics, for example to meet regionally different requirements, as well as to make dynamic settings. Such dynamic settings can i.a. Be provided for event-dependent adjustments as well as an azimuth tracking or compensation for azimuth tracking a nacelle of a wind turbine. Such a flexible flight lighting device is particularly suitable for wind turbines, because on the one hand a high flexibility is needed. On the other hand, wind turbines today have the peculiarity that, although they are not complete, they are essentially standardized and can be set up in completely different regions. The same or almost identical wind energy plant can therefore be provided for completely different regions and can now also be equipped with the same flight lighting facilities. This equipment can already be made before it is clear to which region the respective wind turbine should be delivered. So, before it is clear what regulations the flight lighting device must ultimately meet. Of course, this also includes the case that the delivery of a wind turbine to a specific location and thus a specific region is fixed, but for unpredictable reasons, a change has been made and this wind turbine is now suddenly delivered to another location. This is no longer a problem for the flight beacon of the present invention. It only needs to be adapted accordingly by programming.

4 schematically shows a wind turbine nacelle 402 in a plan view with two flight-lighting devices 400. The flight-beaconing devices 400 are installed on an instrument carrier 404 which is located above the nacelle 402 and can also be walked on for maintenance purposes.

4 shows three rotor blades 406 of the nacelle 402 for illustration only one, namely in a 12 o'clock position. The rotor blade 406 is rotatably arranged together with the spinner 408 to the rest of the nacelle 402. Due to the wind, the rotor blade 406 rotates in the direction of rotation 410 indicated by an arrow. Approaching now an aircraft 412, which is shown here only symbolically and with unrealistically small distance, it can be covered by the rotor blade 406 one of the flight lighting devices 400. Which of the two is hidden, if any obscured depends on the position of the rotor blade 406 and the position of the observer, so here symbolically of the aircraft 412 from.

However, such a problem of the cover by the rotor blade 406 exists only for objects which are located in front of the wind turbine, ie in front of the nacelle 402. If objects are behind the wind turbine or nacelle 402, they can always see both flight beacons 400. It is therefore only necessary for forward that both flight lighting devices 400 radiate in the direction, so provide a double illumination. To the rear, a double illumination by two flight lighting devices 200 is not absolutely necessary. One possibility is that each of the flight beacons radiates 180 ° forward to achieve double illumination because of the problem of coverage by the rotor blade 406. To the rear, both flight lighting devices can each illuminate 90 °, so that together they illuminate 180 ° to the rear, but not twice. To illustrate this, a footprint sector 414 and 416, respectively, are shown for both flight beacons. Each illumination sector 414 or 416 thus illuminates 270 °. Likewise, both flight lighting devices have a blind sector 418 and 420, respectively, in which there is no illumination.

The illumination of the illumination sectors 414 and 416 can now be achieved in a simple manner in that the lighting means or groups of lamps of the flight lighting devices 400 are activated accordingly.

5 shows, by way of example, a vertical emission characteristic of an omnidirectional section, which has four axially spaced luminous means rings. At the ordinate, the light intensity is plotted in candela (Cd), over the vertical angle ranges at the abscissa. The value 0 denotes the respective beam plane and negative values are here upward directions, but this can also be determined differently.

Of the four illuminant rings, only the second to fourth rings counted from below are used for the vertical radiation characteristic shown in FIG. 5, each causing one of the second to fourth individual characteristics 502-504 shown. The first ring can be used for a different characteristic. The overall characteristic 505, which is the sum of the individual characteristics, is also plotted, as well a predetermined setpoint characteristic 506. It can be seen that the setpoint characteristic 506 can be maintained by the overall characteristic 505, which can also be called the sum characteristic.

Fig. 6 shows vertical radiation characteristics for the same omnidirectional section as in Fig. 5, but with a different drive. Here are the first to third ring, counted from below, used. It can be seen that, in comparison to FIG. 5, a different overall characteristic 605 or summation characteristic 605 results, which can comply with the illustrated desired characteristic 606, which is likewise different here. The total characteristic 605 or sum characteristic 605 is the sum of the individual characteristics 601 to 603.

It can also be seen that the single characteristic 602 of the second ring has a higher intensity compared to the single characteristic 502 of FIG. 5, which was also generated by the second ring.

It can thus be seen that the respective overall characteristic or sum characteristic can be influenced or adjusted by the selection of the driven rings, that is to say luminous means rings, as well as by the intensity of the individual activation.

It is thus, not only for the embodiments shown, a variable flight lights, which can also be referred to as obstacle lights or simply as a fire, proposed. Both the intensity and the radiation characteristics of the fire can be changed.

This happens particularly on the switching in and / or switching off of individual LED ^"s or LED groups and / or by different drives. By adding switching and / or switching off the individual ^LEDs or LED groups is particularly the radiation The intensity can be influenced in particular by different activations.

The cause of the change in the fire characteristics may be a sensory value, an automated default, such as a timer, or direct commands, such as remote controls. An example of the application is on-demand nighttime signage. The lights are lit to the minimum necessary to avoid disturbing the residents and to provide adequate protection for the aircraft. When an aircraft is detected, the fire switches to a maximum. This is only an example and it is, for example, also considered and is generally proposed as an embodiment, even with day intensity and / or radiation characteristic depending on an event such as the example mentioned approaching aircraft to change, in particular to adapt to the event.

The utility model should include solutions that are realized in a fire or in several fires.

It is particularly advantageous for the proposed fire that it can be changed in the same operation. The proposed fire can change its setting in normal operation again and again.

Preferably, 4 round beam sections are provided to thereby achieve high flexibility.

In each case, 4 illuminant rings are provided in at least one round-beam section in order to be able to realize very different emission characteristics.

In FIG. 7, a preferred emission characteristic is compared with a previous emission characteristic. Both characteristics are each marked by an upper limit ("max" dashed) and a lower limit (solid "min"), with the respective stronger lines relating to the new, preferred characteristic. Positive values of the vertical emission angles indicate a radiation upward, negative downward and 0 ° denotes a horizontal plane. The specific emission characteristics lie between the upper and lower limits. The previous radiation characteristic is thus substantially evenly distributed around the horizontal plane, whereas the new, preferred radiation characteristic is about the value of 5 °, but it is hardly in the negative region, so hardly radiates down. It is essentially limited to the area upwards.

Claims

claims

1. flight lighting device of a wind turbine for placing on a nacelle of the wind turbine, comprising: at least three circular and concentrically arranged around a common center axis round beam sections and each omnidirectional o o annularly and concentrically arranged around the central axis lens portion having a plane defined perpendicular to the central axis and at least o o a luminous means ring with annularly and concentrically arranged around the central axis bulbs for emitting light through the lens portion, wherein

Is prepared ^■ each illuminant ring for emitting light having an average direction of radiation (370, 371, 372), which relative to the beam plane a beam angle (380, 381, 382), and wherein the emission depends on an axial position of the luminous center ring to the Lens section wherein at least one round-beam section has at least two light-emitting means rings offset axially relative to one another for emitting with different emission angles.

2. Flugbefeuerungseinrichtung according to claim 1, characterized in that the omnidirectional sections are arranged to each other in the axial direction.

3. flight lighting device according to one of the preceding claims, characterized in that the light-emitting means are LEDs.

A flight firing device according to one of the preceding claims, characterized in that at least one or some of the lighting means prepares for emitting light with a first color, in particular red, and at least one further or some further for emitting light with a second color, in particular white are, in particular, that in each case a luminous means ring is provided for emitting a color.

A flight firing device according to one of the preceding claims, characterized in that at least some of the lighting means are designed as red LEDs and have a minimum intensity with a value of the following list:

10cd, 20cd, 25cd, 30cd, 32cd, 50cd, 70cd, 100cd or 200cd.

Flugbefeuerungseinrichtung according to any one of the preceding claims, characterized in that at least some of the lighting means are formed as white LEDs and have a minimum intensity with a value of the following list:

3,4cd, 34cd or 175cd.

A flight-firing device according to one of the preceding claims, characterized in that the flight-firing device has a control unit configured to vary the emission characteristic of the flight-firing device by selective activation of individual light sources, light source groups or light source rings.

Flight firing device according to one of the preceding claims, characterized in that the flight firing device has a control unit, adapted to set or vary an intensity of the lighting means, lighting rings and / or lighting groups.

A flight firing device according to claim 7 or 8, characterized in that the control unit of the flight firing device has fixed programmed emission characteristics.

10. flight firing device according to one of claims 7 to 9, characterized in that the control unit of the flight firing device is prepared to change the emission characteristics during operation of the system, in particular event-dependent.

11. A flight lighting device comprising a rod-shaped main body for horizontally passing through a tower of the wind turbine from inside to outside, or for locating on the outside of the tower, and a lighting section for emitting light for warning aircraft, the lighting section being prepared for only one area above a horizontal plane in which the flight firing device is arranged to illuminate.

12 flight firing device according to one of the preceding claims, characterized in that at least one emission characteristic is firmly implemented.

13. A flight firing device according to any one of the preceding claims, characterized in that at least one or the at least one firmly implemented th emission characteristic radiates substantially only upwards, in particular so that the Flugbefeuerungseinrichtung does not emit downwards when used properly on the wind turbine.

A flight firing device according to one of the preceding claims, characterized in that at least one or the at least one fixedly implemented emission characteristic has a lower emission angle of at least -5 °, in particular approximately -2 °, below this lower emission angle the light intensity being less than 10%, in particular is less than 5% of the maximum light intensity of the radiation characteristic, and / or that the light intensity at an angle of 0 ° is less than 70%, preferably less than 60%, in particular less than 50% of the maximum intensity of the radiation characteristic and in particular with lower radiation angles continues to decrease.

A flight firing device according to any one of the preceding claims, characterized in that at least two fixedly implemented radiation characteristics are provided, of which one is provided for a red night fire and a second for a white day fire.

16 flight firing device according to one of the preceding claims, characterized in that infrared illuminants are provided for emitting infrared light, in particular, that at least one luminous means ring infrared illuminant, in particular infrared LEDs.

17. Wind energy plant with at least one flight firing device according to one of the preceding claims.

18. A method for operating a flight firing device according to one of claims 1 to 16, wherein the lighting means are controlled so that a predetermined radiation characteristic is generated and / or switched on and / or off in a predetermined sector.

19. The method according to claim 18, characterized in that set during operation by appropriate control of the lighting means and / or the light-emitting rings, the properties of the emission of the flight lighting device or changed.

20. The method according to claim 18 or 19, characterized in that during operation, in particular as a function of an event and / or a period or time

a vertical radiation characteristic,

a horizontal sector for emitting and / or a radiation intensity is set or changed,

21. The method according to any one of claims 18 to 20, characterized in that prior to the start-up of the flight-firing device, a radiation characteristic is determined by a determination of the control of the lighting means, in particular light-emitting rings.

22. The method according to any one of claims 18 to 21, characterized in that the flight firing device when on a nacelle of a wind turbine is installed, depending on the azimuth position of the nacelle is readjusted, in particular a varying in the horizontal direction radiation characteristic corresponding to the azimuth position of the nacelle is adapted during operation.